一种双模态超燃燃烧室芯流面积的一维计算方法
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摘要
为了获得双模态超燃冲压发动机一维性能计算的重要参数——燃烧室芯流面积,基于实验测量的壁面静压数据,发展了一种芯流面积的计算方法。计算中,通过选取分离区下游合适的参考截面,获得了燃烧室释热分布模型中的经验常数,从而得到了适用于当前工况的燃烧室芯流面积分布及流动情况,有效地降低了计算方法对来流条件、构型、燃料当量比及喷注方式等多种因素的依赖。与不同工况流场数值仿真结果的对比表明:该方法能够对超燃燃烧室内芯流面积、马赫数的变化情况进行较为准确的捕捉,燃烧效率误差在7%之内,具有较好的通用性。
To obtain the combustor core flow area,which is one of the key factors in the one dimensional calculation of the dual-mode scramjet,a method based on the static pressure measured in the experiment was developed. In this method,the empirical constant,which is suitable for the current condition,of the heat distribution model was obtained through choosing the reference surface downstream of the separation region,and it helped to reduce the dependence on the factors such as the inflow conditions,the configuration of combustor,the equivalence ratio of the fuel,the types of the injection and so on. The comparison with the simulation results indicated that,this method could calculate the core fluid area and Mach number of the scramjet combustor accurately,makethe error of the combustion effect less than 7%,and show good versatility.
To obtain the combustor core flow area,which is one of the key factors in the one dimensional calculation of the dual-mode scramjet,a method based on the static pressure measured in the experiment was developed. In this method,the empirical constant,which is suitable for the current condition,of the heat distribution model was obtained through choosing the reference surface downstream of the separation region,and it helped to reduce the dependence on the factors such as the inflow conditions,the configuration of combustor,the equivalence ratio of the fuel,the types of the injection and so on. The comparison with the simulation results indicated that,this method could calculate the core fluid area and Mach number of the scramjet combustor accurately,makethe error of the combustion effect less than 7%,and show good versatility.
引文
[1]陈强,陈立红,顾洪斌,等.释热分布对超燃冲压发动机性能的影响及优化[J].推进技术,2009,30(2):135-138.(CHEN Qiang,CHEN Li-hong,GUHong-bin,et al.Investigation of the Effect and Optimization of Heat Release Distributions in the Combustor on Scramjet Performance[J].Journalof Propulsion Technology,2009,30(2):135-138.)
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[3]LSENS Radhakrishnan K.Multipurpose Kineties and Sensitivity Analysis Code for Homogeneous Gas-Phase Reactions[J].AIAA Journal,2003,41(2):848-855.
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[12]俞刚,李建国.氢/空气超声速燃烧研究[J].流体力学实验与测量,1999,13(1):1-12.
[13]郭金雷,谷良贤,龚春林.一种改进的冲压发动机一维流分析模型[J].推进技术,2014,35(5):584-590.(GUO Jin-lei,GU Liang-xian,GONG Chun-lin.An Improved One-Dimensional Analysis Model for Ramjet[J].Journal of Propulsion Technology,2014,35(5):584-590.)
[14]张鹏,俞刚.超燃燃烧室一维流场分析模型的研究[J].流体力学实验与测量,2003,17(1):88-92.
[15]程柳维.超声速燃烧室乙烯及其混合燃料点火及火焰特征研究[D].北京:中国科学院力学研究所,2017.
[16]Mitani T,Hiraiwa T,Tarukawa,et al.Drag and TotalPressure Distributions in Scramjet Engines at Mach 8Flight[J].Journal of Propulsion and Power,2002,18(4):953-960.
[17]姜军,初敏,徐旭.双模态超燃燃烧室性能准一维计算方法[J].推进技术,2013,34(6):802-808.(JIANG Jun,CHU Min,XU Xu.A Quasi on Dimensional Method for Prediction of Dual Mode Scramjet Combustor Performance[J].Journal of Propulsion Technology,2013,34(6):802-808.)
[18]Micka D J,Torrez S M,Driscoll J F.Heat Release Distribution in a Dual-Mode Scramjet Combustor-Measurements and Modeling[C].Bremen:16th AIAA/DLR/DG-LR International Space Planes and Hypersonic Systems and Technologies Conference,2009:13-14.
[19]史新兴.基于气动斜坡的超燃燃烧室数值模拟及实验研究[D].北京:北京航空航天大学,2010:73-75.
[20]王辽,韦宝禧,章程亮,等.基于凹腔火焰稳定器的煤油超声速燃烧实验[J].北京航空航天大学学报,2008,34(8):907-910.
[2]Birzer C,Doolan C J.Quasi-One-Dimensional Model of Hydrogen-Fueled Scramjet Combustors[J].Journal of Propulsion Technology,2009,25(6):1220-1225.
[3]LSENS Radhakrishnan K.Multipurpose Kineties and Sensitivity Analysis Code for Homogeneous Gas-Phase Reactions[J].AIAA Journal,2003,41(2):848-855.
[4]王兰,邢建文,郑忠华,等.超燃冲压发动机内流性能的一维评估[J].推进技术,2008,29(6):641-645.(WANG Lan,XING Jian-wen,ZHENG Zhonghua,et al.One-Dimensional Evaluation of the Scramjet Flowpath Performance[J].Journal of Propulsion Technology,2008,29(6):641-645.)
[5]Torrez S M.Preliminary Design Methodology for Hypersonic Engine Flow Paths[C].Bremen:16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference,2009.
[6]李建平,宋文艳,肖隐利.超燃冲压发动机/机体一体化优化设计[J].航空动力学报,2011,26(4):874-879.
[7]Tian L,Chen L H,Chen Q,et al.Quasi-One-Dimensional Multimodes Analysis for Dual-Mode Scramjet[J].Journal of Propulsion and Power,2014,30(6):1559-1567.
[8]刘敬华,凌文辉,刘兴洲,等.超音速燃烧室性能非定常准一维流数值模拟[J].推进技术,1998,19(1):1-6.(LIU Jing-hua,LING Wen-hui,LIU Xing-zhou et al.A Quasi One Dimensional Unsteady Numerical Analysis of Supersonic Combustor Performance[J].Journal of Propulsion Technology,1998,19(1):1-6.)
[9]William H Heiser,David T Pratt.Hypersonic Airbreathing Propulsion[M].Washington DC:AIAA Press,1994.
[10]张栋,唐硕.超燃冲压发动机燃烧室准一维建模与分析[J].弹道学报,2015,27(1):85-91.
[11]Billig F S,Dugger G L,Waltrup P J.Inlet-Combustor Interface Problems in Scramjet Engine[C].France:Proceedings of the First International Symposium on Airbreathing Engines,1972.
[12]俞刚,李建国.氢/空气超声速燃烧研究[J].流体力学实验与测量,1999,13(1):1-12.
[13]郭金雷,谷良贤,龚春林.一种改进的冲压发动机一维流分析模型[J].推进技术,2014,35(5):584-590.(GUO Jin-lei,GU Liang-xian,GONG Chun-lin.An Improved One-Dimensional Analysis Model for Ramjet[J].Journal of Propulsion Technology,2014,35(5):584-590.)
[14]张鹏,俞刚.超燃燃烧室一维流场分析模型的研究[J].流体力学实验与测量,2003,17(1):88-92.
[15]程柳维.超声速燃烧室乙烯及其混合燃料点火及火焰特征研究[D].北京:中国科学院力学研究所,2017.
[16]Mitani T,Hiraiwa T,Tarukawa,et al.Drag and TotalPressure Distributions in Scramjet Engines at Mach 8Flight[J].Journal of Propulsion and Power,2002,18(4):953-960.
[17]姜军,初敏,徐旭.双模态超燃燃烧室性能准一维计算方法[J].推进技术,2013,34(6):802-808.(JIANG Jun,CHU Min,XU Xu.A Quasi on Dimensional Method for Prediction of Dual Mode Scramjet Combustor Performance[J].Journal of Propulsion Technology,2013,34(6):802-808.)
[18]Micka D J,Torrez S M,Driscoll J F.Heat Release Distribution in a Dual-Mode Scramjet Combustor-Measurements and Modeling[C].Bremen:16th AIAA/DLR/DG-LR International Space Planes and Hypersonic Systems and Technologies Conference,2009:13-14.
[19]史新兴.基于气动斜坡的超燃燃烧室数值模拟及实验研究[D].北京:北京航空航天大学,2010:73-75.
[20]王辽,韦宝禧,章程亮,等.基于凹腔火焰稳定器的煤油超声速燃烧实验[J].北京航空航天大学学报,2008,34(8):907-910.